US6881036B2 - Composite integrally bladed rotor - Google Patents

Composite integrally bladed rotor Download PDF

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Publication number
US6881036B2
US6881036B2 US10/235,025 US23502502A US6881036B2 US 6881036 B2 US6881036 B2 US 6881036B2 US 23502502 A US23502502 A US 23502502A US 6881036 B2 US6881036 B2 US 6881036B2
Authority
US
United States
Prior art keywords
pair
bladed rotor
blades
integrally bladed
spar
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime, expires
Application number
US10/235,025
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English (en)
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US20040042902A1 (en
Inventor
David Charles Hornick
Frank J. Euvino, Jr.
James Tyler Roach
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: EUVINO, FRANK J. JR., HORNICK, DAVID CHARLES, ROACH, JAMES TYLER
Priority to US10/235,025 priority Critical patent/US6881036B2/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Priority to JP2003311891A priority patent/JP3940107B2/ja
Priority to AT03255505T priority patent/ATE437293T1/de
Priority to EP20030255505 priority patent/EP1396608B1/de
Priority to DE60328443T priority patent/DE60328443D1/de
Priority to DE2003255505 priority patent/DE03255505T1/de
Publication of US20040042902A1 publication Critical patent/US20040042902A1/en
Priority to US11/007,503 priority patent/US7284957B2/en
Publication of US6881036B2 publication Critical patent/US6881036B2/en
Application granted granted Critical
Assigned to RAYTHEON TECHNOLOGIES CORPORATION reassignment RAYTHEON TECHNOLOGIES CORPORATION CHANGE OF NAME Assignors: UNITED TECHNOLOGIES CORPORATION
Assigned to RAYTHEON TECHNOLOGIES CORPORATION reassignment RAYTHEON TECHNOLOGIES CORPORATION CORRECTIVE ASSIGNMENT TO CORRECT THE AND REMOVE PATENT APPLICATION NUMBER 11886281 AND ADD PATENT APPLICATION NUMBER 14846874. TO CORRECT THE RECEIVING PARTY ADDRESS PREVIOUSLY RECORDED AT REEL: 054062 FRAME: 0001. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF ADDRESS. Assignors: UNITED TECHNOLOGIES CORPORATION
Adjusted expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/15—Two-dimensional spiral
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced

Definitions

  • the present invention relates to an organic matrix composite integrally bladed rotor for use in gas turbine engines.
  • Gas turbine engine discs having integral, radially extending airfoil blades and an integral shroud interconnecting the radially outer extents of the blades is known in the art. Such a construction is shown in U.S. Pat. No. 4,786,347 to Angus. In the Angus patent, the airfoil blades and the disc are formed from an epoxy resin matrix material having chopped carbon fibers therein.
  • U.S. Pat. No. 4,747,900 also to Angus, illustrates a compressor rotor assembly comprising a shaft and at least one disc having integral radially extending airfoil blades, which disc is integral with the shaft.
  • the assembly comprises a matrix material in which a plurality of short reinforcing fibers are so disposed that the majority thereof within the shaft are generally axially aligned while the majority thereof within the airfoil blades are generally radially aligned.
  • At least one filament wound support ring provides radial support for the airfoil blades.
  • an integrally bladed rotor suitable for use in a gas turbine engine broadly comprises a plurality of pairs of airfoil blades with each pair of blades having a spar which extends from a first tip of a first one of the airfoil blades in the pair to a second tip of a second one of the airfoil blades in the pair.
  • the integrally bladed rotor may, or may not, further comprise an outer shroud integrally joined to the first and second tips in each pair of airfoil blades.
  • FIG. 1 is a perspective view of a composite integrally bladed rotor assembly in accordance with the present invention
  • FIG. 2 is a partial sectional view of the integrally bladed rotor assembly of FIG. 1 ;
  • FIG. 3 is a perspective view of a filler ply assembly used in the rotor assembly of FIG. 1 ;
  • FIG. 4 is an exploded view of the integrally bladed rotor assembly of FIG. 1 .
  • FIG. 1 illustrates an integrally bladed rotor assembly 10 in accordance with the present invention.
  • the assembly 10 includes an outer shroud 12 , an inner diameter hub 14 , a stacked ply assembly 16 within the inner diameter hub, and a plurality of pairs of airfoil blades 18 extending between the inner diameter hub 14 and the outer shroud 12 .
  • each pair of airfoil blades 18 has a spar 20 which extends from a first tip 22 of a first one of the airfoil blades 18 in the pair to a second tip 24 of a second one of the airfoil blades 18 in the pair.
  • each spar 20 in a central region has a first arm 26 and a second arm 28 spaced from the first arm 26 and defining an opening 30 with the first arm 26 .
  • the size of the openings 30 will vary from one spar 20 to the next. This allows the spars 20 to be interwoven or interleaved in a spiral pattern. This can be seen by comparing the spar 20 to the spar 20 ′ in FIG. 2 . As the spar 20 runs through the blade 18 , it will taper towards the tip of the blade 18 .
  • the outer shroud 12 and the inner diameter hub 14 may be integrally formed with the airfoil blades 18 .
  • integrally formed a number of advantages are provided. They include the following: (1) blade twist/untwist will be controlled, thus leading to the elimination of stresses at the root of the blade; (2) vibratory frequency of the blade will be increased leading to a reduction in structural requirements and a weight reduction; (3) blade out containment will be integrated into the structure; and (4) blade tip leakage will be eliminated.
  • the integrally formed outer shroud 12 also allows more aggressive forward sweep of the blades 18 .
  • Each of the spars 20 and 20 ′ is preferably formed from an organic matrix composite material having reinforcing fibers running through the center in tension.
  • the continuous reinforcing fibers are so disposed that the majority thereof within the spar 20 and 20 ′ are generally axially aligned with the longitudinal axis of the spar.
  • One material which may be used to form the spars 20 and 20 ′ is an epoxy matrix material having carbon fibers therein.
  • Other materials which may be used may have a matrix formed from a non-organic material such as metal, polyamide, and bismaliamide and/or a fiber reinforcement formed from glass, boron, fiberglass, and KEVLAR.
  • the center of the rotor 10 is filled by a filler ply assembly 16 .
  • the assembly 16 is formed by a plurality of stacked filler plies 32 formed from a near isotropic, fabric lay-up. As can be seen from FIGS. 3 and 4 , the filler plies 32 are arranged in a spiral pattern which matches or compliments the pattern of the spars 20 and 20 ′.
  • the filler ply assembly 30 in addition to filling the center of the rotor 10 , helps distribute the loads on the blades.
  • the rotor design of the present invention provides numerous advantages. For example, by having the spars 20 run through the inner diameter hub 14 between opposing blades 18 , load transfer problems seen in dissimilar material blade/hub designs is eliminated. Further, significant weight savings, i.e. 30% weight reduction, and cost savings, i.e. 75% cost reduction, can be achieved vs. hollow titanium integrally bladed rotors. Also, one can gain major reductions in moment of inertia leading to improved spool up and spool down response.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Ceramic Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Rotary Pumps (AREA)
  • Centrifugal Separators (AREA)
US10/235,025 2002-09-03 2002-09-03 Composite integrally bladed rotor Expired - Lifetime US6881036B2 (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
US10/235,025 US6881036B2 (en) 2002-09-03 2002-09-03 Composite integrally bladed rotor
JP2003311891A JP3940107B2 (ja) 2002-09-03 2003-09-03 一体型ブレード付きロータ
AT03255505T ATE437293T1 (de) 2002-09-03 2003-09-03 Integral beschaufelter rotor
EP20030255505 EP1396608B1 (de) 2002-09-03 2003-09-03 Integral beschaufelter Rotor
DE60328443T DE60328443D1 (de) 2002-09-03 2003-09-03 Integral beschaufelter Rotor
DE2003255505 DE03255505T1 (de) 2002-09-03 2003-09-03 Integral beschaufelter Rotor
US11/007,503 US7284957B2 (en) 2002-09-03 2004-12-08 Composite integrally bladed rotor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/235,025 US6881036B2 (en) 2002-09-03 2002-09-03 Composite integrally bladed rotor

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US11/007,503 Continuation US7284957B2 (en) 2002-09-03 2004-12-08 Composite integrally bladed rotor

Publications (2)

Publication Number Publication Date
US20040042902A1 US20040042902A1 (en) 2004-03-04
US6881036B2 true US6881036B2 (en) 2005-04-19

Family

ID=31715294

Family Applications (2)

Application Number Title Priority Date Filing Date
US10/235,025 Expired - Lifetime US6881036B2 (en) 2002-09-03 2002-09-03 Composite integrally bladed rotor
US11/007,503 Expired - Lifetime US7284957B2 (en) 2002-09-03 2004-12-08 Composite integrally bladed rotor

Family Applications After (1)

Application Number Title Priority Date Filing Date
US11/007,503 Expired - Lifetime US7284957B2 (en) 2002-09-03 2004-12-08 Composite integrally bladed rotor

Country Status (5)

Country Link
US (2) US6881036B2 (de)
EP (1) EP1396608B1 (de)
JP (1) JP3940107B2 (de)
AT (1) ATE437293T1 (de)
DE (2) DE03255505T1 (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050220621A1 (en) * 2002-09-03 2005-10-06 United Technologies Corporation Composite integrally bladed rotor
US20090092842A1 (en) * 2007-10-09 2009-04-09 Hoover Kelly L Article and method for erosion resistant composite
US20090120101A1 (en) * 2007-10-31 2009-05-14 United Technologies Corp. Organic Matrix Composite Components, Systems Using Such Components, and Methods for Manufacturing Such Components
US20090208752A1 (en) * 2008-02-14 2009-08-20 United Technologies Corporation Low transient and steady state thermal stress disk shaped components
US20090263251A1 (en) * 2008-04-16 2009-10-22 Spangler Brandon W Reduced weight blade for a gas turbine engine
US20110182745A1 (en) * 2007-12-28 2011-07-28 Suciu Gabriel L Integrally bladed rotor with slotted outer rim
US10294817B2 (en) 2013-11-21 2019-05-21 United Technologies Corporation Method to integrate multiple electric circuits into organic matrix composite

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US7035535B2 (en) * 2002-08-27 2006-04-25 Pentax Corporation Optical element retracting mechanism for a retractable photographing lens
US7079762B2 (en) 2002-08-27 2006-07-18 Pentax Corporation Supporting structure for supporting a rotatable ring
US7010224B2 (en) * 2002-08-27 2006-03-07 Pentax Corporation Lens barrel incorporating the rotation transfer mechanism
US7027727B2 (en) 2002-08-27 2006-04-11 Pentax Corporation Lens barrel incorporating the cam mechanism
JP2004085934A (ja) * 2002-08-27 2004-03-18 Pentax Corp ズームレンズ鏡筒の繰出カム機構及び繰出カム機構
US6990291B2 (en) * 2002-08-27 2006-01-24 Pentax Corporation Lens barrel having a moving optical element support frame
US7085486B2 (en) * 2002-08-27 2006-08-01 Pentax Corporation Lens barrel incorporating a rotatable ring
US7050713B2 (en) * 2002-08-27 2006-05-23 Pentax Corporation Optical element retracting mechanism for a photographing lens
US6987930B2 (en) * 2002-08-27 2006-01-17 Pentax Corporation Lens barrel incorporating the advancing/retracting mechanism
US7068929B2 (en) 2002-08-27 2006-06-27 Pentax Corporation Optical element retracting mechanism for a retractable lens
US8366047B2 (en) * 2005-05-31 2013-02-05 United Technologies Corporation Electrothermal inlet ice protection system
GB2427658B (en) 2005-06-30 2007-08-22 Rolls Royce Plc Organic matrix composite integrally bladed rotor
DE102005034435B3 (de) 2005-07-14 2007-02-22 Deutsches Zentrum für Luft- und Raumfahrt e.V. Rotor
US7537430B2 (en) * 2005-11-11 2009-05-26 General Electric Company Stacked reaction steam turbine rotor assembly
US8075274B2 (en) * 2009-05-13 2011-12-13 Hamilton Sundstrand Corporation Reinforced composite fan blade
US9080448B2 (en) 2009-12-29 2015-07-14 Rolls-Royce North American Technologies, Inc. Gas turbine engine vanes
CN101913238B (zh) * 2010-08-19 2013-04-17 芜湖纽麦特新材料有限公司 一种挤出设备
US9045990B2 (en) * 2011-05-26 2015-06-02 United Technologies Corporation Integrated ceramic matrix composite rotor disk geometry for a gas turbine engine
US8905719B2 (en) 2011-12-20 2014-12-09 General Electric Co. Composite rotor and vane assemblies with integral airfoils
DE202012009739U1 (de) 2012-10-12 2012-11-05 Abb Turbo Systems Ag Integral gegossenes Turbinenrad
US20140169972A1 (en) * 2012-12-17 2014-06-19 United Technologies Corporation Fan with integral shroud
US20140212261A1 (en) * 2012-12-19 2014-07-31 United Technologies Corporation Lightweight shrouded fan
US9212663B2 (en) * 2013-01-28 2015-12-15 Terrence O'Neill All-supersonic ducted fan for propelling aircraft at high subsonic speeds
WO2014143305A1 (en) 2013-03-14 2014-09-18 United Technologies Corporation Low speed fan for gas turbine engines
US9869198B2 (en) 2015-05-13 2018-01-16 General Electric Company Intershaft integrated seal and lock-nut
US9976429B2 (en) 2015-06-09 2018-05-22 General Electric Company Composite disk
US10047763B2 (en) 2015-12-14 2018-08-14 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling

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Publication number Priority date Publication date Assignee Title
US3403844A (en) * 1967-10-02 1968-10-01 Gen Electric Bladed member and method for making
US3456917A (en) * 1964-01-15 1969-07-22 Rolls Royce Bladed rotor,particularly for a compressor
US4098559A (en) * 1976-07-26 1978-07-04 United Technologies Corporation Paired blade assembly
US4747900A (en) 1984-07-07 1988-05-31 Rolls-Royce Plc Method of manufacture of compressor rotor assembly
US4786347A (en) 1984-07-07 1988-11-22 Rolls-Royce Plc Method of manufacturing an annular bladed member having an integral shroud

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US2857094A (en) * 1955-07-19 1958-10-21 John R Erwin Integral plastic rotors
GB1089162A (en) * 1966-01-10 1967-11-01 Rolls Royce Method of making a bladed rotor member for a fluid flow machine
US6008727A (en) * 1998-09-10 1999-12-28 Xerox Corporation Selectively enabled electronic tags
US6881036B2 (en) * 2002-09-03 2005-04-19 United Technologies Corporation Composite integrally bladed rotor

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3456917A (en) * 1964-01-15 1969-07-22 Rolls Royce Bladed rotor,particularly for a compressor
US3403844A (en) * 1967-10-02 1968-10-01 Gen Electric Bladed member and method for making
US4098559A (en) * 1976-07-26 1978-07-04 United Technologies Corporation Paired blade assembly
US4747900A (en) 1984-07-07 1988-05-31 Rolls-Royce Plc Method of manufacture of compressor rotor assembly
US4786347A (en) 1984-07-07 1988-11-22 Rolls-Royce Plc Method of manufacturing an annular bladed member having an integral shroud

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7284957B2 (en) * 2002-09-03 2007-10-23 United Technologies Corporation Composite integrally bladed rotor
US20050220621A1 (en) * 2002-09-03 2005-10-06 United Technologies Corporation Composite integrally bladed rotor
US8231958B2 (en) 2007-10-09 2012-07-31 United Technologies Corporation Article and method for erosion resistant composite
US20090092842A1 (en) * 2007-10-09 2009-04-09 Hoover Kelly L Article and method for erosion resistant composite
US20090120101A1 (en) * 2007-10-31 2009-05-14 United Technologies Corp. Organic Matrix Composite Components, Systems Using Such Components, and Methods for Manufacturing Such Components
US20110182745A1 (en) * 2007-12-28 2011-07-28 Suciu Gabriel L Integrally bladed rotor with slotted outer rim
US9133720B2 (en) 2007-12-28 2015-09-15 United Technologies Corporation Integrally bladed rotor with slotted outer rim
US8043684B2 (en) 2008-02-14 2011-10-25 United Technologies Corporation Low transient and steady state thermal stress disk shaped components
US8128866B2 (en) 2008-02-14 2012-03-06 United Technologies Corporation Low transient and steady state thermal stress disk shaped components
US20090208752A1 (en) * 2008-02-14 2009-08-20 United Technologies Corporation Low transient and steady state thermal stress disk shaped components
US20090263251A1 (en) * 2008-04-16 2009-10-22 Spangler Brandon W Reduced weight blade for a gas turbine engine
US8282354B2 (en) 2008-04-16 2012-10-09 United Technologies Corporation Reduced weight blade for a gas turbine engine
US10294817B2 (en) 2013-11-21 2019-05-21 United Technologies Corporation Method to integrate multiple electric circuits into organic matrix composite

Also Published As

Publication number Publication date
EP1396608A3 (de) 2005-11-16
EP1396608B1 (de) 2009-07-22
DE60328443D1 (de) 2009-09-03
DE03255505T1 (de) 2004-10-21
EP1396608A2 (de) 2004-03-10
US20050220621A1 (en) 2005-10-06
JP2004092654A (ja) 2004-03-25
ATE437293T1 (de) 2009-08-15
JP3940107B2 (ja) 2007-07-04
US7284957B2 (en) 2007-10-23
US20040042902A1 (en) 2004-03-04

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